Gas turbines are used in various applications, mainly for land-based power generation and aircraft propulsion. In the aviation industry, the fundamental challenge is to increase cycle efficiency while keeping emissions at the lowest possible levels. Main emissions from gas turbine engines include mixed oxides of nitrogen (NOx), carbon monoxide (CO), unburned hydrocarbons (UHC), and particulate matter. The control strategies for emissions are often conflicting in nature; for example, CO or UHC can be reduced by burning the fuel near stoichiometry, but this would lead to high temperatures that have an increased propensity for NOx. Similarly, a lean operation is a solution to reduce NOx emission, but it leads to inefficient combustion leading to an increase in other emissions. Therefore, changing the combustors' existing design to improve one aspect is very difficult without affecting any other performance parameter. Thus, new combustor designs or concepts like lean premixed combustion, lean direct injection, rich-burn quick-quench lean-burn combustion were introduced to meet the performance criteria. The present work focuses on explaining the characteristics of a novel lean direct injection-based burner, known as LDI-3AB, with distributed fuel injection surrounded by airflow through multiple swirlers. Stereoscopic particle image velocimetry (sPIV) was used to characterize the non-reacting flow fields in the axial plane of the burner at different axial distances from the burner plate. The averaged flow fields indicated that the burners have strong swirls and also exhibit good swirl interaction. Each swirler creates a primary recirculation zone. Owing to the interaction between the adjacent swirlers, a shearing region is formed, resulting in secondary recirculation zones between the swirlers. The primary and secondary recirculation can cause proper mixing and help in sustaining the flame and reducing thermal NOx formation.